Performance limit analysis of Recooled Cycle for regenerative cooling systems

In this article, a re-cooled cycle (RCC) has been proposed for a regeneratively cooled scramjet to decrease the hydrogen fuel flow for cooling. In this method, the fuel heat sink (cooling capacity) is indirectly increased, and the fuel onboard is adequate to satisfy the cooling requirement for the whole hypersonic vehicle; this is done instead of carrying excess fuel for cooling or looking for a new coolant. Heat transfer effectivenesses of the cooling passage and pressure loss are introduced in the cycle, and cycle parameters are recomputed. An investigation of the effects of various irreversible losses on the RCC performance is carried out.

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“…From equations ( 3) and ( 22), the definition of the reduction ratio of fuel flow in reference [26] for cooling ϕ can be written as…”

Section: Fig 2 the T -S Diagram Of The Rccmentioning

confidence: 99%

Irreversible cycle analysis of a re-cooled cycle for a scramjet

Qin

Zhou

Bao

et al. 2010

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Considering the severe heat load on the high temperature engine wall, as well as the electric power need on aircraft, it is attractive for designers to establish a thermoelectric conversion system (hereinafter referred to as TECS). Bao et al (2009) proposed a Re-cooling cycle TECS using hydrocarbon fuel as the coolant. They found that this system can reduce the mass flow rate of fuel needed for cooling process.…”

Section: Introductionmentioning

confidence: 99%

The influence of working pressure on the heat transfer process and heat absorption of supercritical CO2 in thermoelectric conversion system

Yang¹,

Wang²,

Niu³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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The influence of working pressure, which is one of the most important parameters in the design of thermoelectric conversion system, on the heat transfer process and heat absorption of supercritical CO2 in the square heated duct is numerically studied. Under the calculated cases, two main vortices with opposite flow direction are formed at the inlet of the heated section. Accordingly, due to the effect of two main vortices, the local heat transfer coefficient profiles on bottom and up wall are M shaped. Meanwhile, it is founded that one wall temperature peak is presented near the inlet of heated duct. With the increase of working pressure, the wall temperature peak decreases gradually. For the safety of the system, it is better to choose 15 MPa as the working pressure due to the relatively low wall temperature peak and pressure. To evaluate the heat absorbed by working fluid, the one-dimensional steady heat transfer model is built. It is found that the absorbed heat changes non-monotonically and the maximum, namely 1080.11 W, is reached under 10 MPa. From the point of heat absorption, it is better to choose 10 MPa as working pressure.

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“…This article advances an open cooling cycle (OCC) for a scramjet based on the thermodynamic principle, a possible alternative to the effective use of the limited resources available to reduce the fuel flow for cooling [13,14]. The temperature of fuel is decreased after the heat of the fuel coming out from the first cooling outlet is converted into mechanical energy, and the fuel is further used for secondary cooling.…”

Section: Introductionmentioning

confidence: 99%

Performance cycle analysis of an open cooling cycle for a scramjet

Qin

Bao

Zhou

et al. 2009

Proceedings of the Institution of Mechanical Engineers, Part G:

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In a conventional regeneratively cooled scramjet, fuel directly enters the combustor after cooling. It is proposed in this article that high-temperature and high-pressure fuel out of the first cooling passage can be used for secondary cooling after expanding through the turbine and transferring enthalpy from fuel to work. A fuel heat sink (cooling capacity) is thus repeatedly used to indirectly increase the fuel heat sink. Instead of carrying excess fuel for cooling or looking for any new coolant, the fuel flow for cooling is reduced, and fuel onboard is adequate to satisfy the cooling requirement for the whole hypersonic vehicle. First are defined cooling and expansion and, second, cooling an open cooling cycle (OCC) for the scramjet. This article provides a brief description of the assessment of the performance potential and scientific feasibility of a scramjet with OCC using fundamental thermodynamic principles. The results show that OCC yields higher performance gain over regenerative cooling, because of the increase in the fuel heat sink and additional power output.

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Performance limit analysis of Recooled Cycle for regenerative cooling systems

Cited by 25 publications

References 24 publications

Irreversible cycle analysis of a re-cooled cycle for a scramjet

Irreversible cycle analysis of a re-cooled cycle for a scramjet

The influence of working pressure on the heat transfer process and heat absorption of supercritical CO2 in thermoelectric conversion system

Performance cycle analysis of an open cooling cycle for a scramjet

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